Patent Application
20190249566
The present invention relates to turbine engines, and more specifically to impingement cooling features for a gas turbine.
In an industrial gas turbine engine, hot compressed gas is produced. The hot gas flow is passed through a turbine and expands to produce mechanical work used to drive an electric generator for power production. The turbine generally includes multiple stages of stator vanes and rotor blades to convert the energy from the hot gas flow into mechanical energy that drives the rotor shaft of the engine. Turbine inlet temperature is limited by the material properties and cooling capabilities of the turbine parts.
A combustion system receives air from a compressor and raises it to a high energy level by mixing in fuel and burning the mixture, after which products of the combustor are expanded through the turbine.
Gas turbines are becoming larger, more efficient, and more robust. Large blades and vanes are being produced, especially in the hot section of the engine system. These hot sections, or hot path sections, have components exposed to hot turbine flow and experience high temperatures. One common approach to cooling parts in the hot section of a gas turbine is to use impingement jets of colder air onto the hot part. The target surface upon which the jet impinges is flat and is on the cold side of the part as shown in
As gas turbine efficiency is increased, one can increase the firing temperature which in turn increases the metal temperature of the hot section parts or reduce the cooling flow, which also leads to increase in hot section metal temperatures.
In one aspect of the present invention, an impingement cooling system for a gas turbine engine comprises: an initial impingement surface with a centrally located opening; a plurality of channels extending radially outward from the opening and formed by a plurality of fixtures that each separates each adjacent channel; wherein the plurality of fixtures each have a rounded upstream end in a plane parallel relative to the initial impingement surface located along an edge of the centrally located opening and a rounded downstream end in the plane parallel relative to the initial impingement surface located along an edge of the initial impingement surface; wherein the plurality of fixtures each have a middle portion between a base portion connected to the initial impingement surface and a top portion on an opposite side; wherein the plurality of fixtures each have a concave shape along the middle portion of the fixture along a plane perpendicular to the initial impingement surface; wherein the plurality of channels are divided into a plurality of sub-channels extending radially outward of an inlet of each channel from a stagnation point created in the channel at an upstream end of a sub-fixture; wherein each of the plurality of sub-fixtures have a rounded upstream end and a generally flat downstream end located along the edge of the initial impingement surface; wherein the plurality of sub-fixtures each have a middle portion between a base portion connected to the initial impingement surface and a top portion on an opposite side; wherein each of the plurality of sub-fixtures each have a concave shape along a middle portion of the sub-fixture along a plane perpendicular to the initial impingement surface.
An advantage of the impingement cooling features includes the shape of the channels and sub-channels to guide the flow towards multiple stagnation points to increase the heat transfer, while keeping the flow within the channels and sub-channels.
Another advantage includes having a plurality of spherical shaped fixtures along the initial impingement surface along the sub-channels, further increasing the turbulence and cooling efficiency of the system.
These and other features, aspects and advantages of the present invention will become better understood with reference to the following drawings, description and claims.
The invention is shown in more detail by help of figures. The figures show preferred configurations and do not limit the scope of the invention.
In the following detailed description of the preferred embodiment, reference is made to the accompanying drawings that form a part hereof, and in which is shown by way of illustration, and not by way of limitation, a specific embodiment in which the invention may be practiced. It is to be understood that other embodiments may be utilized and that changes may be made without departing from the spirit and scope of the present invention.
Broadly, an embodiment of the present invention provides an impingement cooling system for a gas turbine engine includes an initial impingement surface with a centrally located opening. A plurality of channels and plurality of sub-channels extends radially outward from the opening and are formed by a plurality of fixtures and plurality of sub-fixtures that each separates each adjacent channel and sub-channel respectively. The plurality of fixtures and plurality of sub-fixtures each have a rounded upstream end in a plane parallel relative to the initial impingement surface. The plurality of fixtures and the plurality of sub-fixtures each have a concave shape along a middle portion of the fixture and sub-fixture along an axis perpendicular to the initial impingement surface. The plurality of channels is divided into the plurality of sub-channels extending radially outward of an inlet of each channel from a stagnation point created in the channel at an upstream end of a sub-fixture.
A gas turbine engine may comprise a compressor section, a combustor and a turbine section. The compressor section compresses ambient air. The combustor combines the compressed air with a fuel and ignites the mixture creating combustion products comprising hot gases that form a working fluid. The working fluid travels to the turbine section. Within the turbine section are circumferential alternating rows of vanes and blades, the blades being coupled to a rotor. Each pair of rows of vanes and blades forms a stage in the turbine section. The turbine section comprises a fixed turbine casing, which houses the vanes, blades and rotor.
Increasing the ability of the flow to cool a part without increasing mass flow is desirable. Embodiments of the present invention provide impingement cooling features for gas turbine components that may allow for a reduction in losses. Ring segments, blades, vanes, platforms, and other components of a turbine engine may have surfaces that may be cooled through the following impingement cooling system.
Referring now to
The details of an exemplary embodiment of the impingement cooling system and contoured impingement surface are shown in
In certain embodiments, the shape of the each fixture 16 may initially curve inward on each side and expand and then narrow again closer to the downstream end 20 along the plane parallel relative to the initial impingement surface 10 as is shown in
The plurality of channels 14 may then be divided into a plurality of sub-channels 22. The plurality of sub-channels 22 may extend radially outward of an inlet of each channel 14 from a stagnation point 34 created in the channel 14 at an upstream end 26 of a sub-fixture 24. There may be a plurality of sub-fixtures 24. Each sub-fixture 24 includes an upstream end 26 and a downstream end 28. Each sub-fixture upstream end 26 may be rounded. The downstream end 28 of each sub-fixture 24 may be located along the edge 30 of the initial impingement surface 10. Each of the plurality of sub-fixtures 24 may include a concave shape along a middle portion 56 of each sub-fixture 24. The concave shape may be along an axis perpendicular to the initial impingement surface 10. The middle portion 56 of each sub-fixture 24 is between a base portion 58 and a top portion 60. The base portion 58 is connected to the initial impingement surface 10 and the top portion 60 is on an opposite side. In certain embodiments, the base portion 58 and the top portion 60 of each sub-fixture 24 may flare out providing an upper and lower ledge to the sub-fixture 24. In certain embodiments, each sub-fixture 24 may have a roughly triangular shape.
In certain embodiments, a plurality of spherical shaped fixtures 36 may be positioned within each sub-channel 22 along the initial impingement surface 10 and extending into each sub-channel 22. At least one raised spherical shaped fixture 36 may be positioned along the initial impingement surface 10 and extending upward into the radially outer exit section 38 along the edge 30 of the initial impingement surface 10 within each sub-channel 22.
In at least one embodiment, the impingement cooling system may include eight channels 14 and sixteen sub-channels 22 as is shown in
The opening 12 is the first point of contact for cooling fluid, such as, but not limited to, air, from the cooling jet 42. Once the cooling fluid makes contact with the opening 12 along the initial impingement surface 10, the fluid then makes a roughly 90 degree turn. Cooling flow is then driven through the plurality of channels 14 of the contoured surface after stagnating on the flat centrally located opening 12 portion. The top portion 46 of each fixture 16 and top portion 60 of each sub-fixture 24 assist the cooling flow through the plurality of channels 14 and plurality of sub-channels 22 and help to maintain the flow through the plurality of channels 14 and plurality of sub-channels 22. The plurality of channels 14 may guide flow and provide multiple impingement surfaces cooling the overall surface of the component 48. The cooling fluid flows through the plurality of channels 14 and then hits another stagnation point 34 along each of the sub-fixtures 24. The cooling flow will at least impinge on the upstream end 18 of each fixture 16 and stagnation point 34 of each sub-fixture 24. Further, in certain embodiments, the plurality of spherical shaped fixtures 36 may additionally provide further impingement points within the plurality of sub-channels 22 to further decrease flow rate and improve heat transfer. The plurality of spherical shaped fixtures 36 may be along the initial impingement surface 10 along the sub-channels 22, and may further be along the exit section 38 of each sub-channel 22. The cooling flow eventually exits out the radially outer exit section 38 along the edge 30 of the initial impingement surface 10. The geometry of each channel 14 increases the total surface areas for the cooling to occur. Heat transfer and the heat transfer rate may increase with the addition of the plurality of fixtures 16, the plurality of sub-fixtures 24, and the plurality of spherical shaped fixtures 36.
This effect may be explained referring to
The physical contours and lines of the improved impingement surface cannot be manufactured with conventional casting methods. Technology that combines stack lamination with certain molding processes can be used as a casting process that may allow for the detail required for embodiments of the present invention. Selective Laser Melting (SLM) is another example of a manufacturing method. The flow stays longer within the channels 14 created with the contoured surface in embodiments of the present invention.
While specific embodiments have been described in detail, those with ordinary skill in the art will appreciate that various modifications and alternative to those details could be developed in light of the overall teachings of the disclosure. Accordingly, the particular arrangements disclosed are meant to be illustrative only and not limiting as to the scope of the invention, which is to be given the full breadth of the appended claims, and any and all equivalents thereof.
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/US2016/049349 | 8/30/2016 | WO | 00 |
